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-   -   Varying Inlet Angle of Attack for Structured Hexahedral C-Grid around an Airfoil (http://www.cfd-online.com/Forums/cfx/77383-varying-inlet-angle-attack-structured-hexahedral-c-grid-around-airfoil.html)

Josh June 22, 2010 02:46

Varying Inlet Angle of Attack for Structured Hexahedral C-Grid around an Airfoil
 
Hi all -

This topic has been covered several times in various forms.
http://www.cfd-online.com/Forums/cfx...ttack-cfx.html
http://www.cfd-online.com/Forums/cfx...mcfd-hexa.html
http://www.cfd-online.com/Forums/cfx...angle-cfx.html

However, I'd still like a little more information.

I've created a "structured" (the quotations are there because CFX does not accept structured meshes, so it's technically an unstructured hexahedral) C-grid in ICEM-CFD. I'm wondering two things:

1) In terms of my inlet boundary condition, I believe the proper implementation would involve specifying the curved section (O-grid) as the inlet. In the picture below, this is the sloppy red line.

http://img339.imageshack.us/img339/2496/grid1r.png

The green lines are periodic conditions. The blue line is a specified static pressure. Would this be the best way to implement the boundary conditions?

2) I'm going to be parameterizing the angle of attack. I know there are several ways to change the AoA. Since I'm happy with my mesh and spent countless hours on it, I'd rather not rotate the geometry, whether that geometry is the airfoil itself or the airfoil within a cylindrical domain that acts as a stationary rotor with a GGI connection to a larger domain. Both of those methods would require re-meshing, which I'd like to avoid.

I would rather just change the inlet conditions to reflect the new AoA, as shown below.

http://img231.imageshack.us/img231/4958/grid2g.png

I'm afraid that although this second method is simpler, it would cause problems. For one thing, the incoming flow would not be orthogonal to the sides of the cells at the leading edge of the airfoil, as shown below. I believe that this may cause numerical errors or an altered AoA compared to the desired value.

http://img691.imageshack.us/img691/6130/grid3.png

Additionally, I'm sure there are other issues I'm not taking into consideration at the moment (I'm exhausted).

Essentially, I'm wondering if my simple AoA parameterization method is an accurate enough way to simulate changing AoA, or if I should do it differently. Although various journal submissions specify they use a C-grid, they never mention where they implement certain boundary conditions or why.

mach000 June 22, 2010 04:21

Hi,
I think your ideas to change the AoA are the best.
You can't think to remesh everytime you need to change the angle of attack.
Obviously when the AoA increases, the quality of mesh decreases but if the AoA is not so big it is not a problem.
I think you are studying tubulents flow fields. A way to check the quality of mesh, when you change the AoA, is to verify the y+ value. You will note that, increasing the AoA, also the y+ will increase. When y+ value will go over its desiderable value, you have to remesh.
Let me know!

Josh June 22, 2010 12:11

Thanks for the response.

I assume that the AoA changes the y+ because y+ is dependent on friction velocity, which is proportional to shear stress, which is proportional to du/dy. As AoA increases, so, too, would the velocity gradient, correct?

I will likely be modelling from 0 < AoA < 12 degrees, since we will be modelling stall in the low Reynolds number flow regime. I'll check my y+ values as I go along. Just out of personal experience, do you think 12 degrees is too large of an angle and that the mesh quality will be significantly affected?

I know from literature that somewhere around 8 degrees, I'll have to switch from steady to unsteady simulations in order to capture the intermittent bursting of the laminar separation bubble. Perhaps I'll switch meshes at that time, too.

mach000 June 22, 2010 12:37

You are right, about y+ but if your simulation is laminar, y+ as no sense.
about the angle of attack, 12 degrees is probably not so big to change the mesh, but i think it depend by the difference between the numerical and experimental, or theoretical results.
About unsteady simulation, obviously, if you need to capture an intermittent phenomenum, you need an unsteady simulation.
You can run steady simulation until the Cl increases. When you notice that it decreases, you can switch to an unsteady simulation

Josh June 22, 2010 13:49

Thanks for the advice!

I'll be modeling in the transitional regime, so the flow over the airfoil will be laminar to a certain point, then transitioning, then fully turbulent toward the trailing edge.

Josh June 22, 2010 13:50

Also, are my boundary conditions appropriate? I'm not really asking in terms of what they are, but rather where they are. That is, is my periodic condition correct where it is, or should it be extended to the left to cover more of the curved region (therefore reducing the inlet flow area)?

mach000 June 22, 2010 14:07

the BC are the same that I usually use...so I think they could be good.
Transitional simulation, ok. I had some simulation like your some years ago but on a flat plane.
It's not very simple to calculate the transition points on the airfoil. You need to use SST turbulent model and the y+ as to be less than 1

Josh June 22, 2010 14:25

Yes, my max y+ value will be less than one and I will be using either the SST-SAS model with Gamma Theta Transitioning or the SST-DES model. I have read several papers that produced excellent results with both. The original SST and DES models alone are insufficient for transition prediction in flows with significant amounts of separation. The SST is too diffusive and the DES will fail if the timesteps and grid are insufficiently refined. Conversely, the SST-DES and SST-SAS have a fail-safe - if the gird and/or timestep are too coarse, the model will switch from LES to RANS.

mach000 June 22, 2010 14:34

if I remember well I used SST-SAS model with gamma theta and I remember well that you have to pay attention to the turbulent level at the inflow

Josh June 22, 2010 14:56

You do remember well! The model is extremely sensitive to the freestream (inlet) turbulence due to its reliance on the omega equation for resolving the near-wall flow.

ghorrocks June 22, 2010 20:01

Your AOA approach is fine. Just do a sensitivity study to check that your boundaries are far enough away for the accuracy you require.

Josh June 22, 2010 21:27

Will do. I'll be performing sensitivity checks on the domain size, mesh resolution, mesh quality, freestream turbulence intensity, and the turbulence model and its parameters.

My starting domain has a farfield of 20 chords. According to the literature, that should be sufficient, but I'll be sure to check it.


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